EP2619507B1 - Combustor with a single limited fuel-air mixing burner and recuperated micro gas turbine - Google Patents
Combustor with a single limited fuel-air mixing burner and recuperated micro gas turbine Download PDFInfo
- Publication number
- EP2619507B1 EP2619507B1 EP11773910.2A EP11773910A EP2619507B1 EP 2619507 B1 EP2619507 B1 EP 2619507B1 EP 11773910 A EP11773910 A EP 11773910A EP 2619507 B1 EP2619507 B1 EP 2619507B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- air
- inlet
- fuel
- combustor
- stabilization device
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 238000002156 mixing Methods 0.000 title claims description 14
- 239000000446 fuel Substances 0.000 claims description 59
- 239000007789 gas Substances 0.000 claims description 43
- 230000006641 stabilisation Effects 0.000 claims description 35
- 238000011105 stabilization Methods 0.000 claims description 35
- 238000002485 combustion reaction Methods 0.000 claims description 20
- 238000002347 injection Methods 0.000 claims description 5
- 239000007924 injection Substances 0.000 claims description 5
- 238000000034 method Methods 0.000 claims description 2
- 238000001816 cooling Methods 0.000 description 6
- 239000000203 mixture Substances 0.000 description 4
- 238000010438 heat treatment Methods 0.000 description 3
- 239000007788 liquid Substances 0.000 description 3
- 230000015572 biosynthetic process Effects 0.000 description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 238000010790 dilution Methods 0.000 description 1
- 239000012895 dilution Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 230000001052 transient effect Effects 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN A CARRIER GAS OR AIR
- F23C6/00—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion
- F23C6/04—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion in series connection
- F23C6/045—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion in series connection with staged combustion in a single enclosure
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/34—Gas-turbine plants characterised by the use of combustion products as the working fluid with recycling of part of the working fluid, i.e. semi-closed cycles with combustion products in the closed part of the cycle
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/10—Air inlet arrangements for primary air
- F23R3/12—Air inlet arrangements for primary air inducing a vortex
- F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/34—Feeding into different combustion zones
- F23R3/346—Feeding into different combustion zones for staged combustion
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/44—Combustion chambers comprising a single tubular flame tube within a tubular casing
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN A CARRIER GAS OR AIR
- F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
- F23C2900/03001—Miniaturized combustion devices using fluid fuels
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Life Sciences & Earth Sciences (AREA)
- Sustainable Development (AREA)
Description
- The invention relates to a combustor comprising:
- a casing having a cylindrical wall provided with an opening for compressed air;
- a liner being within said casing and having a further cylindrical wall at a distance from the casing wall, an outlet opening on one end and an inlet opening on the other end; and
- a single burner comprising a fuel injector, flame stabilization device and the hardware of the liner inlet (liner head).
- A combustor is known from
US2010/0126174A , and also fromWO01/18371A1 - Other combustors are known from
US2009/019855A1 ,US2010/000218A1 ,US2010/071377A1 , andWO 00/75573A1 - Yet another combustor is known from
US2002/148232A1 , which has multiple burners. None of the individual burners is capable to ensure adequate combustion performance at all operating conditions. Different burners, also in different combinations, have to operate at different operating conditions. - A suitable combustion chamber for a recuperated micro gas turbine is challenged by the following factors:
- Combustor pressure loss has to remain low. With the low compressor pressure ratio of recuperated micro turbines, pressure loss substantially penalizes the power output and efficiency. Typically, the relative burner pressure loss cannot exceed 2%.
- Emission of undesirable chemicals has to be low, namely UHC, CO and NOx. CO and UHC can be effectively oxidized if flow temperature is maintained above 1500 °C (-1800 K). At these temperatures, NOx formation accelerates. However, NOx has to be maintained at single-digit ppm.
- Stable and complete combustion has to be maintained along with low NOx at all operating points between base load and part load. At the same time, stable, complete and low NOx operation has to be guaranteed at light- off and during transients with both cold and hot recuperator.
- It is an object of the present invention to provide a combustor which is optimized for:
- Operation in a recuperated micro gas turbine;
- Low pressure loss;
- Complete combustion and therefore low emission of CO and UHC;
- Low emission of NOx;
- Stable and low-emission operation at base load (with hot recuperator);
- Stable and low-emission operation at part load;
- Reliable light-off at cold conditions (with cold recuperator);
- Reliable light-off at other conditions;
- Stable and low-emission operation during transients;
- Stable and low-emission operation at other conditions; and
- Low cost.
- To this end, in the combustor according to the invention, the relative position of the fuel injector and flame stabilization device in the burner is such that during operation the burner stages first complete combustion of the fuel in the air through the air passages of the flame stabilization device where fuel is injected and then mixing of burned gases with the air through the neighboring passages such that NOx can never increase above single-digit ppm.
- The fuel injector position relative to the flame stabilization device is chosen as to:
- On the one hand, give the necessary residence time for the fuel to combust in the air through the air passages where fuel is injected; and
- On the other hand, mix in the air through the neighboring passages before high NOx levels have been formed.
- In other words, the burner according to the invention stages first combustion of the fuel in the given part of the air and then mixing of burned gases with the remaining air. In particular, combustion is complete and mixing occurs such that NOx can never increase above single-digit ppm.
- The fuel injector is present in the middle of the liner inlet opening, and the flame stabilization device is present in the inlet opening around the fuel injector and extends directly from the fuel injector to the boundary wall of the inlet opening.
- Further, the flame stabilization device comprises two concentrically cylindrical rings and vanes extending in the radial direction from one ring to the other ring and being at an angle with the axial direction, wherein an air passage is present between two neighboring vanes of the flame stabilization device, and the geometry of the said rings, vanes and air passages results in a pressure loss over the flame stabilization device less than 1.5%.
- The flame stabilization device has a swirl strength and air passage cross section such that the pressure loss over the device is less than 1.5%. The pressure loss is dependent, among other parameters, on the geometry of the air passages, the flow rate and the flow density. The geometry of the air passages determines the swirl strength. Contrary to the common knowledge and experience, it has been established and confirmed experimentally that stable burning can be maintained in the combustor according to the invention even when the pressure loss is between 1% and 1.5%.
- The flame stabilization device and the fuel injector form together with the liner inlet hardware a single burner, which guarantees both stable and complete combustion and low NOx at all operating regimes - steady state and transient. The same single burner guarantees reliable light-off at all conditions encountered in operation. This single burner is not assisted by any other burner.
- Still further, the number of vanes in the flame stabilization device is such that only part of the air through the flame stabilization device can mix with fuel.
- An air passage is present between each two neighboring vanes of the flame stabilization device. The fuel injector is provided with injection holes that inject fuel into a number of the air passages such that the fuel is injected only in one passage from each set of two neighboring passages. Such fuel injection allows limited fuel-air mixing, where fuel is mixed with only part of the air. Due to this, the fuel-air mixture formed in the passages where fuel is injected is optimal for high stability of burning. However, high NOx levels can also form in the burned gases. Formation of high NOx levels is prevented though, by quick mixing of these burned gases with the air that passes through the neighboring passages.
- The invention further relates to a recuperated micro gas turbine comprising:
- an air compressor having an air inlet and an air outlet;
- a recuperator having an inlet and outlet for gases to be preheated and an inlet and outlet for hot gases to be cooled, wherein the inlet for gases to be heated is connected to the outlet of the air compressor;
- a combustor according to the invention described above having an air inlet and an outlet for burned gases, wherein the inlet is being connected to the outlet of gases heated in the recuperator;
- a fuel delivery device (a compressor in case of gaseous fuels and a pump in case of liquid fuels) connected to the combustor; and
- a turbine having an inlet connected to the outlet of the combustor and an outlet connected to the inlet of the gases to be cooled in the recuperator.
- The invention further relates to a method for operating a gas turbine according to the invention, wherein the temperature of gases coming from the turbine is kept constant at the recuperator inlet. By this, the flame stabilization is improved at part-load operating points where the shaft power is less than at the base-load operating point. This improvement is realized by limiting reduction in the fuel-air ratio associated with modulation of the gas turbine from the base load to part load.
- There is a great potential for employing micro gas turbines in an electrical power range from 1 kWe to 5 kWe. In particular, micro gas turbines are environmentally and cost effective for distributed power and/or heat and/or cooling generation in households, hotels, farms, restaurants, offices, etc., as well as for vehicular applications.
- The recuperated micro gas turbine according to the invention can be for:
- Electrical power generation systems.
- The use in combined heat and electrical power systems, wherein the gas turbine drives an electrical generator to produce electrical power, and the heat in the gas turbine exhaust is - optionally - utilized for heating, such as space heating, water heating, etc. The heat can be also utilized to produce cooling.
- The use in various heat and power systems in combination with other energy conversion devices, such as fuel cells, Rankine engines, etc.
- The use in auxiliary systems in automotive, maritime and other vehicles.
- The invention will be further elucidated below on the basis of drawings. These drawings show an embodiment of the combustor, combustor burner and recuperated micro gas turbine according to the invention. In the drawings:
-
Figure 1 shows an embodiment of the recuperated micro gas turbine according to the invention; -
Figure 2 shows the combustor of the recuperated micro gas turbine; -
Figure 3 shows the flame stabilization device of the combustor; -
Figure 4 shows the fuel injector of the combustor; and -
Figure 5 shows a burner of the combustor in cross section composed of the flame stabilization device, fuel injector and liner inlet/head hardware. - In
Figure 1 , an embodiment of the recuperated micro gas turbine is shown according to the invention. The recuperated micro gas turbine 1 comprises anair compressor 3, acombustor 5, a fuel compressor 7 (for gaseous fuels) or a pump (for liquid fuels), arecuperator 9 and aturbine 11. The turbine drives the air compressor via ashaft 13. The excess mechanical power produced by the turbine is converted into electrical power in agenerator 15. The generator is either coupled to the turbine- compressor shaft or has its rotor mounted on the turbine-compressor shaft. After the recuperator, the gases can be directed either to a gas-to-water heat exchanger 17 or other equipment for either heat or cooling production. - The
combustor 5, seeFigure 2 , typically receivesair 19 compressed in the gas turbine air compressor and preheated in the recuperator.Fuel 21 to the combustor is delivered by either fuel compressor (for gaseous fuels) or fuel pump (for liquid fuels). The geometric envelope of the combustor is delimited by thecasing 23. The air flow is diffused in thecasing inlet diffuser 25 and dumped into the casing. Inside the casing, a liner 27 (or flame tube) is mounted. The inlet orhead 28 of the liner is equipped with aflame stabilization device 29. The liner is also equipped with a system of air admission holes 31 and cooling arrangements. Combustion is staged inside the liner. The air flow is divided between theflame stabilization device 29, cooling arrangement and air admission holes 31. Thefuel injector 33 is usually located in the vicinity of theflame stabilization device 29. The air flow through the flame stabilization device is usually the combustion air. Fuel is injected and mixed with this air. Theflame stabilization device 29,fuel injector 33 and liner inlet/head hardware 28 are commonly referred to as burner. Theflame 35 is stabilized downstream thefuel stabilization device 29. After combustion has been either fully or essentially completed, the air through the air admission holes 31 is mixed with the products of combustion. This air is called dilution air. Cooling air is gradually mixed with the gases.Diluted gases 37 are directed into the turbine at thecombustor outlet 39. - In
Figure 3 , theflame stabilization device 29 is shown. The flame stabilization device comprises two concentrically cylindrical rings 41 and 43 and a number ofvanes 45 extending in radial direction from one ring to the other ring and being at an angle with theaxial direction 47.Air passages 49 are present between the vanes. - In
Figure 4 , thefuel injector 33 of the combustor is shown. The fuel injector comprises a number of injection holes 51 over the circumference of the injector such that fuel is only injected into half the number of air passages in the flame stabilization device, whereby fuel is injected alternately in one passage and no fuel is injected in the next passage. - In
Figure 5 , a cross section of the burner composed of the flame stabilization device, fuel injector and liner head hardware is shown. The position of thefuel injector 33 relative to theflame stabilization device 29 is chosen for optimal limited fuel-air mixing. It allows the burner to stage first complete combustion of the fuel in the given part of the air and then mixing of burned gases with the remaining air such that NOx can never increase above single-digit ppm.
Claims (5)
- Combustor (5) comprising:- a casing (23) having a cylindrical wall provided with an opening for compressed air;- a liner (27) being within said casing (23) and having a further cylindrical wall at a distance from the casing wall, an outlet opening on one end and an inlet opening on the other end; and- one single burner comprising a fuel injector (33) to inject fuel (21) into the liner (27) and a flame stabilization device (29) comprising air passages (49),wherein the relative position of the fuel injector (33) and flame stabilization device (29) in the burner is such that during operation the burner stages first complete combustion of the fuel (21) in the air through the air passages (49) of the flame stabilization device (29) where fuel (21) is injected and then mixing of burned gases with the air through the neighboring passages (49), wherein the fuel injector (33) is present in the middle of the liner inlet opening, and the flame stabilization device (29) is present in the inlet opening around the fuel injector (33) and extends directly from the fuel injector (33) to the boundary wall of the inlet opening, wherein the flame stabilization device (29) comprises two concentrically cylindrical rings (41, 43) and vanes (45) extending in the radial direction from one ring to the other ring and being at an angle with the axial direction, wherein an air passage (49) is present between two neighboring vanes (45) of the flame stabilization device (29), and the geometry of the said rings (41, 43), vanes (45) and air passages (49) results in a pressure loss over the flame stabilization device (29) less than 1.5%, and wherein the fuel injector (33) is provided with injection holes (51) which during operation inject fuel into the airflow through a part of the total number of the air passages (49).
- Combustor (5) according to claim 1, wherein the injection holes (51) are arranged over the circumference of the fuel injector (33) such that fuel (21) is only injected into half the number of air passages (49) in the flame stabilization device (29).
- Recuperated micro gas turbine (1) comprising:- an air compressor (3) having an air inlet and an air outlet;- a recuperator (9) having an inlet and outlet for gases to be preheated and an inlet and outlet for hot gases to be cooled, wherein the inlet for gases to be heated is connected to the outlet of the air compressor (3);- a combustor (5) according to claim 1 or 2 having an air inlet and an outlet for burned gases, wherein the inlet is connected to the outlet of gases heated in the recuperator (9),- a fuel delivery device connected to the combustor (5), and- a turbine (11) having an inlet connected to the outlet of the combustor (5) and an outlet connected to the inlet of the gases to be cooled of the recuperator (9).
- Recuperated micro gas turbine (1) according to claim 3, wherein the burner of the combustor (5) is the single and non-assisted burner in the recuperated micro gas turbine (1).
- Method for operating a recuperated gas turbine (1) according to claim 3, wherein the temperature of gases coming from the turbine (11) is kept constant at the recuperator inlet.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
NL2005381A NL2005381C2 (en) | 2010-09-21 | 2010-09-21 | Combustor with a single limited fuel-air mixing burner and recuperated micro gas turbine. |
PCT/NL2011/050636 WO2012039611A1 (en) | 2010-09-21 | 2011-09-20 | Combustor with a single limited fuel-air mixing burner and recuperated micro gas turbine |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2619507A1 EP2619507A1 (en) | 2013-07-31 |
EP2619507B1 true EP2619507B1 (en) | 2019-11-06 |
Family
ID=44201365
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP11773910.2A Active EP2619507B1 (en) | 2010-09-21 | 2011-09-20 | Combustor with a single limited fuel-air mixing burner and recuperated micro gas turbine |
Country Status (4)
Country | Link |
---|---|
US (1) | US20130213050A1 (en) |
EP (1) | EP2619507B1 (en) |
NL (1) | NL2005381C2 (en) |
WO (1) | WO2012039611A1 (en) |
Families Citing this family (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CA2940592A1 (en) * | 2013-02-26 | 2014-09-04 | Electric Jet, Llc | Micro gas turbine engine for powering a generator |
FR3041742B1 (en) * | 2015-09-30 | 2017-11-17 | Ifp Energies Now | COMBUSTION CHAMBER FOR A TURBINE, IN PARTICULAR A THERMODYNAMIC CYCLE TURBINE WITH RECUPERATOR, FOR THE PRODUCTION OF ENERGY, ESPECIALLY ELECTRICAL ENERGY. |
FR3049044B1 (en) * | 2016-03-18 | 2019-12-20 | IFP Energies Nouvelles | COMBUSTION CHAMBER OF A TURBINE, IN PARTICULAR OF A THERMODYNAMIC CYCLE TURBINE WITH RECUPERATOR, FOR THE PRODUCTION OF ENERGY, PARTICULARLY ELECTRICAL ENERGY. |
CN106247403B (en) * | 2016-08-02 | 2019-08-02 | 北京航空航天大学 | A kind of miniature gas turbine combustion chamber of double-wall structure |
FR3055403B1 (en) | 2016-08-29 | 2021-01-22 | Ifp Energies Now | COMBUSTION CHAMBER WITH A HOT COMPRESSED AIR DEFLECTOR, ESPECIALLY FOR A TURBINE INTENDED FOR ENERGY PRODUCTION, ESPECIALLY ELECTRICAL ENERGY |
FR3055404B1 (en) | 2016-08-29 | 2021-01-22 | Ifp Energies Now | MODULAR TURBINE, ESPECIALLY A TURBINE WITH HEAT EXCHANGER FOR ENERGY PRODUCTION, ESPECIALLY ELECTRICAL ENERGY |
USD910717S1 (en) | 2018-07-31 | 2021-02-16 | Hotstart, Inc. | Rotary atomizer |
US20200041130A1 (en) | 2018-07-31 | 2020-02-06 | Hotstart, Inc. | Combustor Systems |
US11156164B2 (en) | 2019-05-21 | 2021-10-26 | General Electric Company | System and method for high frequency accoustic dampers with caps |
US11174792B2 (en) | 2019-05-21 | 2021-11-16 | General Electric Company | System and method for high frequency acoustic dampers with baffles |
US11824424B2 (en) | 2021-09-10 | 2023-11-21 | Hamilton Sundstrand Corporation | Combined integrated waste heat recovery and inlet pressure boost system |
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US3853273A (en) * | 1973-10-01 | 1974-12-10 | Gen Electric | Axial swirler central injection carburetor |
EP1445465A1 (en) * | 2003-02-06 | 2004-08-11 | The Boeing Company | Combination of core engine with ramjet engine incorporating swirl augmented combustion |
EP2085695A1 (en) * | 2008-01-29 | 2009-08-05 | Siemens Aktiengesellschaft | Fuel nozzle with swirl duct and method for manufacturing a fuel nozzle |
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USRE23149E (en) * | 1949-09-20 | Combustion burner | ||
JPS4724483Y1 (en) * | 1970-12-22 | 1972-08-02 | ||
US4274253A (en) * | 1977-12-22 | 1981-06-23 | The Garrett Corporation | Control for turbine and recuperator inlet temperatures |
US5163287A (en) * | 1989-12-22 | 1992-11-17 | Sundstrand Corporation | Stored energy combustor with fuel injector containing igniter means for accommodating thermal expansion |
US5373694A (en) * | 1992-11-17 | 1994-12-20 | United Technologies Corporation | Combustor seal and support |
FR2706985B1 (en) * | 1993-06-22 | 1995-08-25 | Pillard Ent Gle Chauffage Indl | |
US5477685A (en) * | 1993-11-12 | 1995-12-26 | The Regents Of The University Of California | Lean burn injector for gas turbine combustor |
FR2774152B1 (en) * | 1998-01-28 | 2000-03-24 | Inst Francais Du Petrole | COMBUSTION CHAMBER OF GAS TURBINE OPERATING ON LIQUID FUEL |
JP3364169B2 (en) | 1999-06-09 | 2003-01-08 | 三菱重工業株式会社 | Gas turbine and its combustor |
US6298654B1 (en) * | 1999-09-07 | 2001-10-09 | VERMES GéZA | Ambient pressure gas turbine system |
US6453658B1 (en) | 2000-02-24 | 2002-09-24 | Capstone Turbine Corporation | Multi-stage multi-plane combustion system for a gas turbine engine |
US6745574B1 (en) * | 2002-11-27 | 2004-06-08 | Elliott Energy Systems, Inc. | Microturbine direct fired absorption chiller |
JP3940705B2 (en) | 2003-06-19 | 2007-07-04 | 株式会社日立製作所 | Gas turbine combustor and fuel supply method thereof |
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-
2010
- 2010-09-21 NL NL2005381A patent/NL2005381C2/en not_active IP Right Cessation
-
2011
- 2011-09-20 EP EP11773910.2A patent/EP2619507B1/en active Active
- 2011-09-20 WO PCT/NL2011/050636 patent/WO2012039611A1/en active Application Filing
-
2013
- 2013-03-21 US US13/848,276 patent/US20130213050A1/en not_active Abandoned
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3853273A (en) * | 1973-10-01 | 1974-12-10 | Gen Electric | Axial swirler central injection carburetor |
EP1445465A1 (en) * | 2003-02-06 | 2004-08-11 | The Boeing Company | Combination of core engine with ramjet engine incorporating swirl augmented combustion |
EP2085695A1 (en) * | 2008-01-29 | 2009-08-05 | Siemens Aktiengesellschaft | Fuel nozzle with swirl duct and method for manufacturing a fuel nozzle |
Also Published As
Publication number | Publication date |
---|---|
WO2012039611A1 (en) | 2012-03-29 |
US20130213050A1 (en) | 2013-08-22 |
EP2619507A1 (en) | 2013-07-31 |
NL2005381C2 (en) | 2012-03-28 |
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